CN112810811A - A dual-rotor drone - Google Patents
A dual-rotor drone Download PDFInfo
- Publication number
- CN112810811A CN112810811A CN202110069727.5A CN202110069727A CN112810811A CN 112810811 A CN112810811 A CN 112810811A CN 202110069727 A CN202110069727 A CN 202110069727A CN 112810811 A CN112810811 A CN 112810811A
- Authority
- CN
- China
- Prior art keywords
- ducted fan
- dual
- rotor
- tilting
- unmanned aerial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
本申请实施例涉及一种双旋翼无人机，包括：包括机身、共轴双旋翼、固定翼、倾转涵道风扇和混合动力系统，共轴双旋翼设置在机身的顶部，倾转涵道风扇有两个，通过固定翼对称设置在机身的两侧，混合动力系统设置在机身内部，且混合动力系统与共轴双旋翼以及倾转涵道风扇连接，以驱动共轴双旋翼以及倾转涵道风扇，倾转涵道风扇能够在混合动力系统的驱动下绕所述机身转动。能够根据实际情况进行共轴双旋翼和涵道风扇的调节，以完成无人机的垂直起降和水平飞行，以及降低飞机的飞行阻力，以提高无人机的航程，采用混合动力系统驱动共轴双旋翼和涵道风扇，能够使功率分配更加合理，以降低油耗，提高无人机的航速，增大无人机的航程和航时。
The embodiment of the present application relates to a dual-rotor UAV, comprising: a fuselage, a coaxial dual-rotor, a fixed wing, a tilting ducted fan and a hybrid power system, the coaxial dual-rotor is arranged on the top of the fuselage, and the tilting There are two ducted fans, which are symmetrically arranged on both sides of the fuselage through the fixed wings. The hybrid power system is set inside the fuselage, and the hybrid power system is connected with the coaxial dual rotors and the tilting ducted fan to drive the coaxial dual rotors. and a tilting ducted fan, which can rotate around the fuselage driven by the hybrid power system. It can adjust the coaxial dual rotors and ducted fans according to the actual situation to complete the vertical take-off and landing and horizontal flight of the drone, as well as reduce the flight resistance of the aircraft to improve the range of the drone. The dual-axis rotors and ducted fans can make the power distribution more reasonable to reduce fuel consumption, increase the speed of the drone, and increase the range and flight time of the drone.
Description
Technical Field
The application relates to the technical field of aircraft manufacturing, particularly, relate to a two rotor unmanned aerial vehicle.
Background
The vertical take-off and landing aircraft is almost not limited by the field, can take off and land on any flat ground, can be deployed at a position closer to a battlefield, is much convenient and quick for transporting personnel and materials, and greatly improves the efficiency of combined delivery; and the probability of hitting by enemy army is greatly reduced because the device is not limited by the field.
At present, vertical take-off and landing aircrafts are mainly divided into two main categories: rotorcraft and fixed-wing aircraft. Among them, rotorcraft are typically represented by helicopters owned by the major military forces of the world. Such as the apache helicopters, the kmann helicopters, the konu dry transport helicopters, the new generation high speed helicopters S-97, etc., the russian card series helicopters, etc., the chinese helicopter in the straight line, etc.
However, the maximum takeoff weight of the existing helicopter is directly limited by the power of an engine, and after the helicopter vertically flies, rotates and flies horizontally, the power requirement is further improved and the oil consumption is increased due to the increase of resistance, so that the range of the helicopter is greatly influenced, and the hitting capability of the helicopter on a deep target is weak.
Disclosure of Invention
The embodiment of the application provides a two rotor unmanned aerial vehicle aims at solving the current less problem of gyroplane range.
The embodiment of the application provides a wind power generation system which comprises a fuselage, coaxial double rotors, fixed wings, a tilt ducted fan and a hybrid power system;
the coaxial double rotors are arranged at the top of the fuselage;
the two tilting ducted fans are symmetrically arranged on two sides of the machine body through the fixed wings;
the hybrid power system is arranged in the fuselage and connected with the coaxial dual rotors and the tilting ducted fan to drive the coaxial dual rotors and the tilting ducted fan;
the tilting ducted fan can wind the body under the driving of the hybrid power system.
Optionally, the tilt ducted fan comprises a tilt mechanism and a ducted fan;
the ducted fan is connected with the fixed wings through a tilting mechanism, and one ends of the fixed wings, far away from the ducted fan, are connected with the fuselage;
the hybrid power system is respectively connected with the tilting mechanism and the ducted fan.
Optionally, the hybrid powertrain system includes a multiple-engine, parallel-drive deceleration system and an electric propulsion system;
the multiple parallel-engine deceleration system is connected with the electric propulsion system;
the multiple parallel-engine deceleration system is connected with the coaxial double rotors;
the electric propulsion system is connected with the ducted fan;
the tilting mechanism is connected with the multiple-parallel-car deceleration system and/or the electric propulsion system.
Optionally, the multiple parallel operation deceleration system comprises an engine and a deceleration mechanism;
the number of the engines is N, the output shaft of each engine is in transmission connection with the speed reducing mechanism, the speed reducing mechanism is connected with the coaxial double rotors and the tilting ducted fan, and N is a positive integer not less than 2.
Optionally, the multiple-parallel-running deceleration system further comprises a plurality of starting and power generation integrated motors, and each engine is connected with one starting and power generation integrated motor;
the electric propulsion system includes a battery and a power module;
the storage battery is electrically connected with the power module, and the power module is connected with the tilting ducted fan and the starting and power generation integrated motor.
Optionally, the coaxial dual rotors comprise an upper rotor, a lower rotor, an outer rotor shaft, and an inner rotor shaft;
the outer rotor shaft is sleeved outside the inner rotor shaft;
the upper rotor wing is connected with the inner rotor wing shaft, and the lower rotor wing is connected with the outer rotor wing shaft.
Optionally, the reduction mechanism comprises an upper gear and a lower gear;
the upper gear and the lower gear are vertically and coaxially mounted to the tooth surface;
the outer rotor shaft penetrates through the middle part of the upper gear and is fixedly connected with the upper gear;
the inner rotor shaft penetrates through the middle part of the lower gear and is fixedly connected with the lower gear;
and a power input cylindrical gear is connected to an output shaft of each engine, is arranged between the upper gear and the lower gear and is in meshed driving with the upper gear and the lower gear.
Optionally, horizontal stabilizers are symmetrically connected to the rear ends of the two sides of the fuselage.
Optionally, a vertical fin is connected to an end of the horizontal tail wing, which is far away from the fuselage.
Optionally, a landing gear mechanism is provided at the bottom of the fuselage.
By adopting the dual-rotor unmanned aerial vehicle provided by the application, on the first hand, the coaxial dual rotors are arranged at the top of the fuselage, the number of the tilting ducted fans is two, the tilting ducted fans are symmetrically arranged at two sides of the fuselage through the fixed wings, the hybrid power system is arranged in the fuselage, and the hybrid power system is connected with the coaxial dual rotors and the tilting ducted fans so as to drive the coaxial dual rotors and the tilting ducted fans, the tilting ducted fans can rotate around the fuselage under the drive of the hybrid power system, wherein the two tilting ducted fans are symmetrically arranged at two sides of the fuselage through the fixed wings, the tilting ducted fans can rotate around the fuselage under the drive of the hybrid power system, when the unmanned aerial vehicle needs to vertically take off, the tilting ducted fans can realize tilting under the drive of the hybrid power system so as to enable the tilting ducted fans to be in the vertical direction, and further provide upward thrust under the drive of the hybrid power, so as to reduce the oar dish area of coaxial two rotors, thereby reduce the radius of rotation and the flight resistance of coaxial two rotors, when unmanned aerial vehicle needs horizontal flight, the ducted fan that verts can realize verting under hybrid power system's drive, so that the ducted fan that verts is in the horizontal direction, and the ducted fan that verts can provide horizontal thrust under hybrid power system's drive, thereby accelerates unmanned aerial vehicle's preceding speed of flying.
In the second aspect, hybrid power system with coaxial two rotors and the ducted fan that verts connects, adopts the coaxial two rotors of hybrid power system drive and the ducted fan that verts, can make power distribution more reasonable to reduce the oil consumption, improve the journey and the time of flight of aircraft, in addition, the ducted fan that verts passes through the stationary vane symmetry and sets up in the both sides of fuselage, and the stationary vane can provide partial lift when unmanned aerial vehicle level flight, thereby reduces unmanned aerial vehicle's consumption, promotes unmanned aerial vehicle's horizontal flight speed.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the description of the embodiments of the present application will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without inventive exercise.
Fig. 1 is a schematic side view of a dual-rotor drone according to an embodiment of the present application;
fig. 2 is a schematic diagram of a hybrid power system of a dual rotor drone according to an embodiment of the present application;
fig. 3 is a schematic top view of a dual-rotor drone according to an embodiment of the present application;
fig. 4 is a schematic front view of a dual-rotor drone according to an embodiment of the present application;
fig. 5 is a schematic side view of a dual-rotor drone in a vertical takeoff and landing state according to an embodiment of the present application;
fig. 6 is a schematic view of a deceleration mechanism of a dual-rotor drone according to an embodiment of the present application.
Description of reference numerals:
1-fuselage, 2-coaxial dual rotors, 21-upper rotor, 22-lower rotor, 23-inner rotor shaft, 24-outer rotor shaft, 3-tilting ducted fan, 4-fixed wing, 5-hybrid power system, 51-multiple parallel vehicle speed reducing system, 511-engine, 5111-output shaft of engine, 5112-power input cylindrical gear, 512-speed reducing mechanism, 5121-upper gear, 5122-lower gear, 513-starting power generation integrated motor, 52-electric propulsion system, 521-storage battery, 522-power module, 6-horizontal tail, 7-vertical tail and 8-landing gear mechanism.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
In the related art, vertical take-off and landing aircrafts are mainly classified into two categories: rotorcraft and fixed-wing aircraft. Among them, rotorcraft are typically represented by helicopters owned by the major military forces of the world. Such as the apache helicopters, the kmann helicopters, the konu dry transport helicopters, the new generation high speed helicopters S-97, etc., the russian card series helicopters, etc., the chinese helicopter in the straight line, etc.
However, the maximum takeoff weight of the existing helicopter is directly limited by the power of the engine, and after the helicopter vertically flies, rotates and flies horizontally, the power requirement is further improved and the oil consumption is increased due to the increase of resistance, so that the range of the helicopter is greatly influenced, and the hitting capability of the helicopter on a deep target is weak.
In view of this, this application creatively provides a two rotor unmanned aerial vehicle, aims at solving the current less problem of gyroplane range.
Referring to fig. 1 and fig. 2, fig. 1 is a schematic side view of a dual-rotor unmanned aerial vehicle according to an embodiment of the present application, and fig. 2 is a schematic hybrid power system of the dual-rotor unmanned aerial vehicle according to the embodiment of the present application. As shown in fig. 1 and 2, the dual-rotor unmanned aerial vehicle comprises a fuselage 1, a coaxial dual rotor 2, a fixed wing 4, a tilt ducted fan 3 and a hybrid power system 5;
the coaxial dual rotors 2 are arranged on the top of the fuselage 1;
the two tilting ducted fans 3 are symmetrically arranged on two sides of the machine body 1 through the fixed wings 4;
the hybrid power system 5 is arranged inside the fuselage 1, and the hybrid power system 5 is connected with the coaxial dual rotors 2 and the tilt ducted fan 3 to drive the coaxial dual rotors 2 and the tilt ducted fan 3;
the tilt ducted fan 3 can be driven by the hybrid system 5 to rotate around the body 1.
In the embodiment, two tilting ducted fans 3 are symmetrically arranged on two sides of a fuselage 1 through fixed wings 4, the tilting ducted fans 3 can rotate around the fuselage 1 under the drive of a hybrid power system 5, when an unmanned aerial vehicle needs to take off vertically, the tilting ducted fans 3 can tilt under the drive of the hybrid power system 5 so that the tilting ducted fans 3 are in the vertical direction, and then under the drive of the hybrid power, upward thrust is provided so as to reduce the area of a propeller disc of a coaxial dual-rotor wing 2, thereby reducing the rotating radius and flight resistance of the coaxial dual-rotor wing 2, when the unmanned aerial vehicle needs to fly horizontally, the tilting ducted fans 3 can tilt under the drive of the hybrid power system 5 so that the tilting ducted fans 3 are in the horizontal direction, the tilting ducted fans 3 can provide horizontal thrust under the drive of the hybrid power system 5, thereby quickening the front flying speed of the unmanned aerial vehicle.
Based on above-mentioned two rotor unmanned aerial vehicle, but this application provides following some concrete examples of implementing, under the prerequisite of not contradicting each other, but the arbitrary combination between each example to form a new kind of two rotor unmanned aerial vehicle. It should be understood that a new dual rotor drone, formed by any combination of examples, is intended to fall within the scope of the present application.
Referring to fig. 1 to 5, fig. 3 is a schematic top view of a dual-rotor drone according to an embodiment of the present application, fig. 4 is a schematic front view of a dual-rotor drone according to an embodiment of the present application, and fig. 5 is a schematic side view of a vertical take-off and landing state of a dual-rotor drone according to an embodiment of the present application, where in a possible embodiment, the tilt ducted fan 3 includes a tilt mechanism and a ducted fan;
the ducted fan is connected with the fixed wing 4 through a tilting mechanism, and one end of the fixed wing 4, which is far away from the ducted fan, is connected with the fuselage 1;
and the hybrid power system 5 is respectively connected with the tilting mechanism and the ducted fan.
In the embodiment, the tilt ducted fan 3 comprises a tilt mechanism and a ducted fan, wherein the ducted fan is connected with the fixed wing 4 through the tilt mechanism, one end of the fixed wing 4, which is far away from the ducted fan, is connected with the fuselage 1, the hybrid power system 5 is respectively connected with the tilt mechanism and the ducted fan, the hybrid power system 5 can drive the tilt mechanism, so that the tilt mechanism drives the ducted fan to rotate, wherein, during horizontal flight, the central axis of the ducted fan is parallel to the central axis of the unmanned aerial vehicle, the ducted fan can rotate under the drive of the hybrid power system 5, so as to provide forward thrust, when vertical take-off and landing are required, the hybrid power system 5 can drive the tilt mechanism, so that the tilt mechanism drives the ducted fan to tilt from the horizontal direction to the vertical direction, at this time, the ducted fan can provide upward thrust under the drive of the hybrid power system 5, thereby the coaxial pair of rotor 2 of cooperation realizes unmanned aerial vehicle's VTOL.
In a possible embodiment, the hybrid system 5 comprises a multiple-engine deceleration system 51 and an electric propulsion system 52;
the multiple parallel operation deceleration system 51 is connected with the electric propulsion system 52;
the multiple-engine-parallel-running deceleration system 51 is connected with the coaxial double rotors 2;
the electric propulsion system 52 is connected to the ducted fan;
the tilting mechanism is connected to the multiple parallel operation deceleration system 51 and/or the electric propulsion system 52.
In the present embodiment, the hybrid power system 5 includes a multiple parallel operation deceleration system 51 and an electric propulsion system 52, wherein the multiple parallel operation deceleration system 51 is connected with the electric propulsion system 52 so as to enable the cooperative use and energy recovery of the engine 511 and the electric motor, the multiple parallel operation deceleration system 51 is connected with the coaxial twin rotor 2 so as to enable the coaxial twin rotor 2 to be driven by the hybrid power of the engine 511 and the electric motor, and the electric propulsion system 52 is connected with the ducted fan, wherein the electric propulsion system 52 provides electric energy so as to enable the ducted fan to provide thrust by driving the ducted fan to operate by the electric energy.
The tilting mechanism is connected to the multiple parallel operation deceleration system 51 and/or the electric propulsion system 52, that is, the tilting mechanism can be connected to the multiple parallel operation deceleration system 51 so as to be able to drive the tilting mechanism through the engine 511, for example, the tilting mechanism can include a bearing and a tilting shaft, the bearing is disposed in the fixed wing 4, the tilting shaft passes through the bearing, one end of the tilting shaft is in transmission connection with the multiple parallel operation deceleration system 51, the other end of the tilting shaft is connected to the ducted fan, so that the tilting shaft is driven to rotate by the multiple parallel operation deceleration system 51, and the ducted fan is driven to rotate, the tilting mechanism can also be connected to the electric propulsion system 52 so as to be able to drive the tilting mechanism to rotate by the electric power provided by the battery, so as to drive the ducted fan to rotate, for example, the tilting mechanism can include a servo motor, the servo motor is disposed in the fixed wing 4, and the output, servo motor is connected with electric propulsion system 52, electric propulsion system 52 drive servo motor work, and then drive the culvert fan rotation through servo motor's output shaft, in addition, the mechanism of verting still can include the stopper, the stopper can be connected with the speed reduction system 51 or electric propulsion system 52 that merge frequently, so that when the culvert fan rotated horizontal position or vertical position, fix the culvert fan through the stopper, avoid the culvert fan to take place relative rotation with fuselage 1.
In one possible embodiment, the multiple parallel vehicle deceleration system 51 includes an engine 511 and a deceleration mechanism 512;
the number of the engines 511 is N, an output shaft 5111 of each engine is in transmission connection with the speed reducing mechanism 512, the speed reducing mechanism 512 is connected with the coaxial dual rotors 2 and the tilt ducted fan 3, wherein N is a positive integer not less than 2.
In the present embodiment, the multiple-engine parallel-operation deceleration system 51 includes an engine 511 and a deceleration mechanism 512, where N engines 511 are provided, an output shaft 5111 of each engine is in transmission connection with the deceleration mechanism 512, and the deceleration mechanism 512 is connected with the coaxial dual rotors 2 and the tilt bypass fan 3, where N is a positive integer not less than 2, that is, there may be 2 or more engines 511, and the output shafts 5111 of the multiple engines are in transmission connection with the deceleration mechanism 512 so as to be capable of providing output power simultaneously to drive the coaxial dual rotors 2, thereby increasing the aircraft speed.
In a possible embodiment, the multiple parallel operation deceleration system 51 further comprises a plurality of start-and-power-generation integrated motors 513, and each engine 511 is connected to one start-and-power-generation integrated motor 513;
the electric propulsion system 52 comprises a battery 521 and a power module 522;
the battery 521 is electrically connected to the power module 522, and the power module 522 is connected to the tilt ducted fan 3 and the start-up/power generation integrated motor 513.
In the present embodiment, the multiple-parallel-operation deceleration system 51 further includes a plurality of starting-generating-integrated motors 513, each engine 511 is connected to one starting-generating-integrated motor 513, the starting-generating-integrated motors 513 can start the engines 511, and can generate power under the rotation of the engines 511, to charge the battery 521, the electric propulsion system 52 comprises the battery 521 and a power module 522, wherein the storage battery 521 is electrically connected with the power module 522, the power module 522 is connected with the tilt ducted fan 3 and the start-up power generation integrated motor 513, the electric energy of the storage battery 521 reaches the motor of the ducted fan through the power module 522 to drive the motor of the ducted fan to work, so that the ducted fan operates to provide thrust, the power module 522 can reasonably distribute the power of the multiple engine speed reduction system 51 and the electric propulsion system 52, and the purpose of saving energy is achieved.
In a possible embodiment, the coaxial dual rotor 2 comprises an upper rotor 21, a lower rotor 22, an outer rotor shaft 24 and an inner rotor shaft 23;
the outer rotor shaft 24 is sleeved outside the inner rotor shaft 23;
the upper rotor 21 is connected with the inner rotor shaft 23, and the lower rotor 22 is connected with the outer rotor shaft 24.
In the present embodiment, the coaxial twin rotor 2 includes an upper rotor 21, a lower rotor 22, an outer rotor shaft 24, and an inner rotor shaft 23, wherein the outer rotor shaft 24 is fitted around the outer side of the inner rotor shaft 23, the upper rotor 21 is connected to the inner rotor shaft 23, the lower rotor 22 is connected to the outer rotor shaft 24, so that the upper rotor 21 rotates together with the inner rotor shaft 23, the lower rotor 22 rotates together with the outer rotor shaft 24, and the upper rotor 21 and the lower rotor 22 can separately rotate.
Referring to fig. 1 to 6, fig. 6 is a schematic view of a speed reducing mechanism 512 of a dual-rotor drone according to an embodiment of the present application, where in a possible implementation, the speed reducing mechanism 512 includes an upper gear 5121 and a lower gear 5122;
the upper side gear 5121 and the lower side gear 5122 are installed coaxially with the tooth surface vertical;
the outer rotor shaft 24 passes through the middle part of the upper gear 5121 and is fixedly connected with the upper gear 5121;
the inner rotor shaft 23 passes through the middle of the lower gear 5122 and is fixedly connected with the lower gear 5122;
a power input cylindrical gear 5112 is connected to an output shaft 5111 of each engine, and the power input cylindrical gear 5112 is arranged between the upper gear 5121 and the lower gear 5122 and is in meshed driving with the upper gear 5121 and the lower gear 5122.
In the present embodiment, the reduction mechanism 512 includes an upper gear 5121 and a lower gear 5122, the upper gear 5121 and the lower gear 5122 are coaxially installed with the tooth surfaces thereof facing each other vertically, the outer rotor shaft 24 passes through the middle of the upper gear 5121 and is fixedly connected to the upper gear 5121, the inner rotor shaft 23 passes through the middle of the lower gear 5122 and is fixedly connected to the lower gear 5122, and the upper gear 5121 and the lower gear 5122 are relatively rotatable, so that the outer rotor shaft 24 can be rotated by the upper gear 5121 and the inner rotor shaft 23 can be rotated by the lower gear 5122. A power input cylindrical gear 5112 is connected to the output shaft 5111 of each engine, and the power input cylindrical gear 5112 is arranged between the upper gear 5121 and the lower gear 5122 and is in meshed driving with the upper gear 5121 and the lower gear 5122, so that the output shaft 5111 of each engine can drive the upper gear 5121 and the lower gear 5122 to rotate in opposite directions through the power input cylindrical gear 5112, and the upper rotary wing 21 and the lower rotary wing 22 can rotate in opposite directions.
In a possible embodiment, the rear ends of the two sides of the fuselage 1 are symmetrically connected with horizontal stabilizers 6.
In this embodiment, the horizontal rear wing 6 can improve the balance performance of the unmanned aerial vehicle.
In a possible embodiment, a vertical fin 7 is attached to the horizontal rear wing 6 at the end remote from the fuselage 1.
In this embodiment, the vertical fin 7 can assist the steering of the unmanned aerial vehicle to improve the maneuvering performance of the unmanned aerial vehicle.
In a possible embodiment, the bottom of the fuselage 1 is provided with a landing gear mechanism 8.
In this embodiment, the bottom of fuselage 1 is provided with landing gear mechanism 8 to make things convenient for the support to fuselage 1 when unmanned aerial vehicle rises and falls, avoid fuselage 1 to contact ground and cause the damage.
In a feasible implementation mode, the unmanned aerial vehicle further comprises a scanning imaging and communication radar system, a fire control system and a flight control system, wherein the scanning imaging and communication radar system, the fire control system and the flight control system are all arranged in the machine body 1, so that the practical performance of the unmanned aerial vehicle is improved.
It should be understood that while the present specification has described preferred embodiments of the present application, additional variations and modifications of those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including the preferred embodiment and all such alterations and modifications as fall within the true scope of the embodiments of the application.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or terminal that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or terminal. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or terminal that comprises the element.
The above detailed description is given to the dual-rotor unmanned aerial vehicle provided by the application, and a specific example is applied in the description to explain the principle and the implementation of the application, and the description of the above embodiment is only used to help understand the method and the core idea of the application; meanwhile, for a person skilled in the art, according to the idea of the present application, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present application.
Claims (10)
1. A dual-rotor unmanned aerial vehicle is characterized by comprising a vehicle body (1), coaxial dual rotors (2), fixed wings (4), a tilting ducted fan (3) and a hybrid power system (5);
the coaxial double rotors (2) are arranged at the top of the fuselage (1);
the two tilting ducted fans (3) are symmetrically arranged on two sides of the machine body (1) through the fixed wings (4);
the hybrid power system (5) is arranged inside the fuselage (1), and the hybrid power system (5) is connected with the coaxial dual rotors (2) and the tilt ducted fan (3) to drive the coaxial dual rotors (2) and the tilt ducted fan (3);
the tilting ducted fan (3) can rotate around the machine body (1) under the driving of the hybrid power system (5).
2. Dual rotor unmanned aerial vehicle of claim 1,
the tilting ducted fan (3) comprises a tilting mechanism and a ducted fan;
the ducted fan is connected with the fixed wing (4) through a tilting mechanism, and one end, far away from the ducted fan, of the fixed wing (4) is connected with the machine body (1);
and the hybrid power system (5) is respectively connected with the tilting mechanism and the ducted fan.
3. Twin-rotor unmanned aerial vehicle according to claim 2, wherein the hybrid power system (5) comprises a multiple-engine speed reduction system (51) and an electric propulsion system (52);
the multiple parallel-operation deceleration system (51) is connected with the electric propulsion system (52);
the multiple parallel-operation deceleration system (51) is connected with the coaxial double rotors (2);
the electric propulsion system (52) is connected with the ducted fan;
the tilting mechanism is connected with the multiple parallel vehicle speed reducing system (51) and/or the electric propulsion system (52).
4. Dual rotor unmanned aerial vehicle of claim 1,
the multiple parallel operation deceleration system (51) comprises an engine (511) and a deceleration mechanism (512);
the number of the engines (511) is N, the output shaft (5111) of each engine is in transmission connection with the speed reducing mechanism (512), wherein the speed reducing mechanism (512) is connected with the coaxial double rotors (2) and the tilt ducted fan (3), and N is a positive integer not less than 2.
5. Dual rotor unmanned aerial vehicle of claim 4,
the multiple-parallel-running deceleration system (51) further comprises a plurality of starting and power-generating integrated motors (513), and each engine (511) is connected with one starting and power-generating integrated motor (513);
the electric propulsion system (52) comprising a battery (521) and a power module (522);
the storage battery (521) is electrically connected with the power module (522), and the power module (522) is connected with the tilting ducted fan (3) and the starting and power generation integrated motor (513).
6. Dual rotor unmanned aerial vehicle of claim 4,
the coaxial double rotors (2) comprise an upper rotor (21), a lower rotor (22), an outer rotor shaft (24) and an inner rotor shaft (23);
the outer rotor shaft (24) is sleeved on the outer side of the inner rotor shaft (23);
go up rotor (21) with interior rotor shaft (23) are connected, lower rotor (22) with outer rotor shaft (24) are connected.
7. Dual rotor unmanned aerial vehicle of claim 6,
the reduction mechanism (512) includes an upper gear (5121) and a lower gear (5122);
the upper gear (5121) and the lower gear (5122) are mounted coaxially with their tooth surfaces facing each other vertically;
the outer rotor shaft (24) penetrates through the middle part of the upper gear (5121) and is fixedly connected with the upper gear (5121);
the inner rotor shaft (23) penetrates through the middle part of the lower gear (5122) and is fixedly connected with the lower gear (5122);
a power input cylindrical gear (5112) is connected to an output shaft (5111) of each engine, and the power input cylindrical gear (5112) is arranged between the upper gear (5121) and the lower gear (5122) and is in meshed driving with the upper gear (5121) and the lower gear (5122).
8. Dual rotor unmanned aerial vehicle of claim 1,
the rear ends of the two sides of the machine body (1) are symmetrically connected with horizontal tail wings (6).
9. Dual rotor unmanned aerial vehicle of claim 8,
one end of the horizontal tail (6) far away from the machine body (1) is connected with a vertical fin (7).
10. Dual rotor unmanned aerial vehicle of claim 1,
the bottom of the machine body (1) is provided with a landing gear mechanism (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110069727.5A CN112810811B (en) | 2021-01-19 | 2021-01-19 | Double-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110069727.5A CN112810811B (en) | 2021-01-19 | 2021-01-19 | Double-rotor unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112810811A true CN112810811A (en) | 2021-05-18 |
| CN112810811B CN112810811B (en) | 2023-10-03 |
Family
ID=75870151
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110069727.5A Active CN112810811B (en) | 2021-01-19 | 2021-01-19 | Double-rotor unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112810811B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115200648A (en) * | 2022-09-14 | 2022-10-18 | 四川省亚通工程咨询有限公司 | Bridge state monitoring system and method based on unmanned aerial vehicle |
| CN115352643A (en) * | 2022-08-08 | 2022-11-18 | 北京科技大学 | Multi-parallel-engine coaxial dual-rotor helicopter power assembly based on single-plane gear pair |
| WO2022260634A1 (en) * | 2021-06-07 | 2022-12-15 | Ali Turan | Differential gearbox with output shafts that are on the same side and rotate in reverse directions |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102211663A (en) * | 2011-05-11 | 2011-10-12 | 王略 | Gear tilting type coaxial machine |
| US20170210463A1 (en) * | 2014-10-01 | 2017-07-27 | Sikorsky Aircraft Corporation | Tip clearance measurement of a rotary wing aircraft |
| CN107856488A (en) * | 2017-11-16 | 2018-03-30 | 四川省特种设备检验研究院 | Power transmission system of plug-in hybrid power hovercar capable of taking off and landing vertically |
| CN108528734A (en) * | 2017-03-02 | 2018-09-14 | 贝尔直升机德事隆公司 | Hybrid propulsion drivetrain system for tiltrotor aircraft |
| WO2019184869A1 (en) * | 2018-03-28 | 2019-10-03 | 刘保伸 | Multi-purpose helicopter having dual compartment structure, electronic omni-directional rotor assembly, and application thereof |
| US20200164975A1 (en) * | 2018-11-26 | 2020-05-28 | Bell Helicopter Textron Inc. | Tilting duct compound helicopter |
| CN111483590A (en) * | 2020-05-26 | 2020-08-04 | 清华大学 | Coaxial contra-rotating dual-rotor speed reduction transmission structure |
-
2021
- 2021-01-19 CN CN202110069727.5A patent/CN112810811B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102211663A (en) * | 2011-05-11 | 2011-10-12 | 王略 | Gear tilting type coaxial machine |
| US20170210463A1 (en) * | 2014-10-01 | 2017-07-27 | Sikorsky Aircraft Corporation | Tip clearance measurement of a rotary wing aircraft |
| US20170283047A1 (en) * | 2014-10-01 | 2017-10-05 | Sikorsky Aircraft Corporation | Main rotor rotational speed control for rotorcraft |
| CN108528734A (en) * | 2017-03-02 | 2018-09-14 | 贝尔直升机德事隆公司 | Hybrid propulsion drivetrain system for tiltrotor aircraft |
| CN107856488A (en) * | 2017-11-16 | 2018-03-30 | 四川省特种设备检验研究院 | Power transmission system of plug-in hybrid power hovercar capable of taking off and landing vertically |
| WO2019184869A1 (en) * | 2018-03-28 | 2019-10-03 | 刘保伸 | Multi-purpose helicopter having dual compartment structure, electronic omni-directional rotor assembly, and application thereof |
| US20200164975A1 (en) * | 2018-11-26 | 2020-05-28 | Bell Helicopter Textron Inc. | Tilting duct compound helicopter |
| CN111483590A (en) * | 2020-05-26 | 2020-08-04 | 清华大学 | Coaxial contra-rotating dual-rotor speed reduction transmission structure |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022260634A1 (en) * | 2021-06-07 | 2022-12-15 | Ali Turan | Differential gearbox with output shafts that are on the same side and rotate in reverse directions |
| CN115352643A (en) * | 2022-08-08 | 2022-11-18 | 北京科技大学 | Multi-parallel-engine coaxial dual-rotor helicopter power assembly based on single-plane gear pair |
| CN115200648A (en) * | 2022-09-14 | 2022-10-18 | 四川省亚通工程咨询有限公司 | Bridge state monitoring system and method based on unmanned aerial vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112810811B (en) | 2023-10-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9994305B1 (en) | Coaxial drive propulsion system for aerial vehicles, and associated systems and methods | |
| CN112810811A (en) | A dual-rotor drone | |
| CN107662702B (en) | Hybrid power double-coaxial same-side reverse tilting rotor aircraft | |
| CN102167155B (en) | Aircraft with turnable wings | |
| EP3087003A1 (en) | An unmanned aerial vehicle | |
| CN106927040A (en) | It is a kind of can VTOL the rotor tailless configuration aircraft of tailstock formula four | |
| RU2521090C1 (en) | High-speed turboelectric helicopter | |
| WO2021010915A1 (en) | A multi-function unmanned aerial vehicle with tilting co-axial, counter-rotating, folding propeller system | |
| CN109533319A (en) | A kind of tilting rotor unmanned vehicle structural system with the overlap joint wing | |
| CN105197237A (en) | Vertical takeoff and landing unmanned aerial vehicle | |
| CN106114842B (en) | A kind of oil electricity mixing coaxial dual-rotor helicopter and its application method | |
| CN207374648U (en) | The double coaxial homonymy reversion tiltrotor aircrafts of hybrid power | |
| CN212579543U (en) | Urban air aerocar | |
| CN105173076B (en) | A kind of vertical take-off and landing drone | |
| CN109229360A (en) | Scissor DCB Specimen seesaw type autogyro | |
| CN107662703B (en) | Electric double-coaxial same-side reverse tilting rotor aircraft | |
| CN107021208A (en) | The tail sitting posture VUAV and control method of a kind of utilization duct | |
| CN112046745B (en) | A Portable Modular UAV Platform | |
| CN209305857U (en) | Fixed-wing electric airplane co-axial contra rotating propeller dynamical system and fixed-wing electric airplane | |
| RU2579235C1 (en) | Light convertible high-speed helicopter | |
| RU2529568C1 (en) | Cryogenic electrical convertiplane | |
| CN111532426A (en) | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout | |
| CN206125407U (en) | Miniature ducted fan aircraft | |
| CN114987737A (en) | Tail active variable-pitch ducted propulsion unmanned aerial vehicle | |
| CN207374647U (en) | Electronic double coaxial homonymy reversion tiltrotor aircrafts |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |